Abstract:

A targeting scheme is presented to build trajectories from a specified Earth parking orbit to a specified low lunar orbit via a low-energy transfer and up to two maneuvers. The total transfer ΔV is characterized as a function of the Earth parking orbit inclination and the departure date for transfers to each given low lunar orbit. The transfer ΔV cost is characterized for transfers constructed to low lunar polar orbits with any longitude of ascending node and for transfers that arrive at the Moon at any given time during a month.